U.S. patent application number 11/936499 was filed with the patent office on 2008-03-13 for single/multiple guard(s)/cap(s) and/or screen(s) with engine attached apparatus and/or pole with rotational system(s) - centrifuge chamber/manifold particle collector.
Invention is credited to Marina Ellen Marinella Pavlatos.
Application Number | 20080060325 11/936499 |
Document ID | / |
Family ID | 22606202 |
Filed Date | 2008-03-13 |
United States Patent
Application |
20080060325 |
Kind Code |
A1 |
Pavlatos; Marina Ellen
Marinella |
March 13, 2008 |
SINGLE/MULTIPLE GUARD(S)/CAP(S) AND/OR SCREEN(S) WITH ENGINE
ATTACHED APPARATUS AND/OR POLE WITH ROTATIONAL SYSTEM(S) -
CENTRIFUGE CHAMBER/MANIFOLD PARTICLE COLLECTOR
Abstract
This invention relates in general to a guard(s)/cap(s) and/or
screen(s) apparatus (single and/or multiple formation) for the
nacelle/air inlet for numerous jets, turbojet, turboprop and
turboshaft engines--(Helicopters and other VTOL/VSTOL aircraft)
such as power plants or the like. This apparatus contains the
rotational system(s) as well as the engine shaft attached apparatus
and/or pole that allows the mechanism to function by auto induced
movement, without limiting engine thrust. Additional security
measures have been introduced to the guard(s)/cap(s) and/or
screen(s) apparatus, which includes a centrifuge chamber/manifold
for particle collector without limiting engine thrust.
Inventors: |
Pavlatos; Marina Ellen
Marinella; (Buffalo Grove, IL) |
Correspondence
Address: |
PATENT ADMINISTRATOR;KATTEN MUCHIN ROSENMAN LLP
1025 THOMAS JEFFERSON STREET, N.W.
EAST LOBBY: SUITE 700
WASHINGTON
DC
20007-5201
US
|
Family ID: |
22606202 |
Appl. No.: |
11/936499 |
Filed: |
November 7, 2007 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
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11495743 |
Jul 28, 2006 |
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11936499 |
Nov 7, 2007 |
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10977014 |
Oct 29, 2004 |
7160345 |
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11495743 |
Jul 28, 2006 |
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10148507 |
Jan 9, 2003 |
6872232 |
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PCT/US00/30145 |
Nov 20, 2000 |
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10977014 |
Oct 29, 2004 |
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60167163 |
Nov 23, 1999 |
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Current U.S.
Class: |
55/306 |
Current CPC
Class: |
F02C 7/055 20130101;
B01D 45/14 20130101; B01D 2279/60 20130101; B01D 45/12
20130101 |
Class at
Publication: |
055/306 |
International
Class: |
B01D 46/48 20060101
B01D046/48 |
Claims
1. An air intake guard system for a turbine having a housing for
use in an air intake cavity comprising: one or more guards
configured to be in communication with said air intake cavity in
said housing; a centrifuge chamber; one or more rotating vanes
mounted for rotational movement in said centrifuge chamber, said
vanes configured to conform to a predetermined shape of said air
intake cavity; a passageway in communication with said centrifuge
chamber for collecting foreign particles in said centrifuge
chamber, said passageway formed as part of said housing and
extending axially along said housing; and an outlet chamber in
communication with said centrifuge chamber for discharging said
foreign particles outside of said housing.
2. The system as recited in claim 1, wherein said predetermined
shape is cylindrical.
3. The system as recited in claim 2, wherein said system includes
two guards.
4. The system as recited in claim 1, wherein said two guards are
spaced apart and define said centrifuge chamber therebetween.
5. The system as recited in claim 1, wherein said predetermined
shape is conical.
6. The system as recited in claim 1, wherein said one or more
guards are retractable.
7. An air intake guard system for a turbine for use in an air
intake cavity comprising: one or more guards disposed in said air
intake cavity, said one or more guards mounted for rotational
movement; one or more rotating vanes defining a centrifuge; and a
discharge passageway in communication with said centrifuge for
receiving and discharging articles collected in saved
centrifuge.
8. The system as recited in claim 1, wherein said one or more
rotating vances are configured to be retractable.
9. The system as recited in claim 1, wherein said predetermined
shape is rectangular.
Description
CROSS-REFERENCE TO RELATED APPLICATIONS
[0001] This application is based upon and claims the priority of
U.S. Provisional Patent Application Ser. No. 60/167,163, filed on
Nov. 23, 1999.
BACKGROUND OF THE INVENTION
[0002] 1. Field of the Invention
[0003] The present invention relates to a system for preventing
and/or separation foreign objects from the air intake of a turbine
engine. In particular, this invention relates in general to a
single/multiple guard(s)/cap(s) and/or screen(s) with engine shaft
apparatus and/or pole. Extensions/rods can be laced, for example,
fixed/secured, adhered, positioned and/or attached to the
guard(s)/cap(s) and/or screen(s); as well as to the engine shaft
extension(s) and/or pole apparatus, and/or rotational systems. The
rotational system(s)--functions with complete, pivot and/or partial
movement (for example) for gas separation, for the nacelle/air
inlet of numerous jet engines, turbojet, turboprop and turboshaft
engines such as aircraft and power plants or the like. The addition
of the centrifuge chamber/manifold particle collector with
rotational system(s) would further add security means without
limiting engine thrust.
[0004] 2. Description of the Prior Art
[0005] Problems are caused by ingestion of foreign objects into the
nacelle/air inlet of engines; this problem has been previously
known and recognized, for example, as disclosed in U.S. Pat. Nos.
2,695,074; 2,931,460; 2,944,631; 2,969,941; 3,121,545; 3,148,043;
3,426,981; 3,521,431; 3,616,616; 3,766,719; 3,832,086; 3,871,844;
4,149,689; 4,265,646; 4,617,028; 4,833,879; 5,046,458 and
5,411,224, all hereby incorporated by reference. However, such
systems are known to limit engine thrust thus solving one problem
and creating another. Since jet engines, turbojet, turboprop and/or
turboshaft aircraft operate in environments where foreign objects
cannot be controlled or removed, solutions must be found in order
to solve this problem. Numerous aircraft have reported Such
problems with foreign objects, yet constructive solutions have not
been previously found. Such problems with ingestion of foreign
objects to engines causes damage in the compressor stage and to
other portions of the engine. Such engine damage is immediate by
partial or complete engine thrust surmounting to impairment of
aircraft's flying ability. Since many of the systems used in
aircraft are limited in function of engine capability, for example,
two engines, such limitation can be detrimental and/or fatal. The
possible ingestion of foreign objects in engines during or shortly
after aircraft take-off (ascending) and or aircraft landing
(descent) can be grave consequence.
[0006] The advent of gas turbine helicopters and other vehicles
take-off and landing with VTOL/VSTOL aircraft, foreign
matter-particles are also of grave concert. Helicopters and other
VTOL/VSTOL aircraft are also especially suited for certain low
altitude missions on both land and sea, including combat support,
search and rescue, and ant-submarine warfare; this foreign particle
matter leaves the aircraft in a grave situation. Therefore, it is
desirable to provide means as a guard and a particle collector for
such conditions to ensure safety.
SUMMARY OF THE INVENTION
[0007] This invention relates in general to a guard(s)/cap(s)
and/or screen(s) apparatus (single and/or multiple formation--along
with the manipulations) for the nacelle/air inlet for numerous jet
engines, turbojet, turboprop, turboshaft engines--(Helicopters and
VTOL/VSTOL aircraft) such as aircraft power plants or the like. The
guard(s)/cap(s) and/or screen(s) minimize if not eliminate entry of
foreign objects into the nacelle/air inlet thereby allowing the
function of the aircraft to operate respectively. In order for the
appropriate function to occur gas separation must take place. In
accordance with an important aspect of the invention, system(s) may
be implemented with or without treads/threads (for example)--(along
with the manipulations) that would allow the guard(s)/cap(s) and/or
screen(s) to function accordingly for gas separation. The
rotational system(s) and the guard(s)/cap(s) and/or screen(s),
shall function with the invention of the engine shaft extension(s)
attachment and/or pole apparatus (along with the manipulations).
The invention of the extensions/rods from the guard(s)/cap(s)
and/or screen(s) shall be fixed/secured, adhered, positioned and/or
attached to the rotational system(s) and/or directly to the engine
shaft extension(s) attachment and/or pole apparatus. The engine
shaft extension(s) attachment and/or pole apparatus, with the
extensions/rods from the guard(s)/cap(s) and/or screen(s) shall be
fixed/secured, adhered and/or attached to the inward and/or outward
portion of the guard(s)/cap(s) and/or screen(s)--(along with the
manipulations). Extensions/rods can also be attached
latitudinal/longitudinal and/or laced (for example) on the
guard(s)/cap(s) and/or screen(s) of the rotational system(s). Thus
adhering fixed/ secured and/or positioned to the rotational
system(s) and/or directly to the engine shaft extension(s)
attachment and/or pole apparatus. Opening and Closure of apparatus
can be attained by center axis--for example of the guard(s)/cap(s)
and/or screen(s) in multiple sections (2 and/or odd numbers). Thus
closure can occur upon the engine shaft attached apparatus and/or
pole in a folding or laced process (for example) along with the
extensions/rods. Therefore, allowing continuous motion and/or
function to occur from the engine without obstruction or further
automation nor limiting engine thrust.
[0008] Additional security measures are taken with the centrifuge
chamber/manifold particle collector with or without ejector
system(s), through conduit means. Such additional security system
would ensure any doubt of foreign particle entry and destruction
prior to reaching main engine components--compressor, combustor, a
gas generator turbine for driving the compressor and power turbine
for the driving of an output shaft. Thus, the rotational system(s)
and engine-attached apparatus would ensure continuous motion and/or
function to occur from the engine with further security system
means without limiting engine thrust.
DESCRIPTION OF THE DRAWING
[0009] These and other advantages of the present invention will be
readily understood with reference to the following specification
and attached drawing wherein:
[0010] FIG. 1 shows an isometric view of double guards/caps and/or
screens with engine attached apparatus and/or pole, with rotational
system. Additional security by means of the centrifuge
chamber/manifold particle collector-separator is with rotational
system. Guard/cap and/or screen in the nacelle/air inlet according
to the disclosed embodiment of the present invention;
[0011] FIG. 2 shows an isometric view of the double guards/caps
and/or screens with engine attached apparatus and/or pole, with
rotational system. Centrifuge chamber/manifold particle
collector-separator with the exhibited within the multi vane
conical;
[0012] FIG. 3 shows an isometric partial expanded view of a multi
vane double guards/caps and/or screens with engine attached
apparatus and/or pole, with rotational systems. Centrifuge
chamber/manifold particle collector-separator with shown with
expanded as well as multiple extensions/rods (exhibited in the
inward position towards the security apparatus);
[0013] FIG. 4 shows an isometric partial expanded view of a multi
vane double guards/caps and/or screens with the engine attached
apparatus and/or pole, with rotational systems. Centrifuge
chamber/manifold particle collector-separator with shown with
expanded as well as multiple extensions/rods (exhibited in the
outward position of the security apparatus);
[0014] FIG. 5 shows a cross-sectional view of separator.
[0015] FIG. 6 shows the additional ejector system.
[0016] FIG. 7 shows the manifold sectional, engine attached
apparatus and/or pole--(apparatus can be single, or attached,
fixed,/secured on the engine attached apparatus and/or pole, or
fixed secured on the guard(s)/cap(s) and/or screen(s). The manifold
ma also include a mesh to further allow gas separation to take
place.
[0017] FIG. 8 shows an isometric partial view of the double
guards/caps and/or screens with engine attached apparatus and/or
pole, with rotational systems;
[0018] FIG. 9 shows an isometric partial expanded view of a double
guards/caps and/or screen with engine attached apparatus and/or
pole, with rotational systems;
[0019] FIG. 10 shows an isometric view of a retractable double
guards/caps and/or screens with engine attached apparatus and/or
pole, with rotational systems;
[0020] FIG. 11 shows an isometric partial expanded view of the
double guard/caps and/or screens with engine attached apparatus
and/or pole, with rotational systems; exhibits folding and/or laced
pattern for retraction process;
[0021] FIG. 12 shows dispersing of a conical for retraction
process; conical may take multiple forms.
[0022] FIG. 13 shows dispersing of a conical for retraction
process, additional concial is exhibited which thus also can take
multiple forms.
[0023] FIG. 14 shows dispersing of a conical for retraction
process; additional conical may take multiple forms and vane guard
thus shown in background; aperture of the vane guard shall have
variance in aperture for gas separation.
[0024] FIG. 15 shows the engine shaft extension security attachment
and/or pole, diamond formation (for example).
[0025] FIG. 16 shows the engine shaft extension security attachment
and/or pole cylindrical form (for example).
[0026] FIG. 17 shows the engine shaft extension security attachment
and/or pole, in rectangular form (for example).
[0027] FIG. 18 shows the multiple section engine attachment for
retraction process of the apparatus and/or pole.
[0028] FIG. 19 shows the multiple section engine attachment for
retraction process of the apparatus and/or pole.
[0029] FIG. 20 shows longitudinal apparatus and/or pole for
numerous dual inlets, with a dual extending apparatus from the pole
for inlet--power plants and the like.
[0030] FIG. 21 shows longitudinal apparatus and/or pole for
inlet--power plants and the like.
[0031] FIG. 22 shows longitudinal apparatus and/or pole for
numerous dual inlets, with a dual extending apparatus for both
sides of the pole for the inlet--power plants and the like.
[0032] FIG. 23 rotational ring with serrated form (can also be
inverted).
[0033] FIG. 24 rotational ring with jagged form (can also be
inverted).
[0034] FIG. 25 rotational ring with rectangular form (can also be
inverted).
[0035] FIG. 26 rotational ring with jagged interlocked form (can
also be inverted).
[0036] FIG. 27 rotational ring with interlocked form (can also be
inverted).
[0037] FIG. 28 rotational ring as coiled form (can also be inverted
without ring but in ring formation--for example as well as numerous
coils).
[0038] FIG. 29 rotational ring as slotted form (can also be
inverted on the outside as well as internal portion of the
ring--for example as well as numerous slots).
[0039] FIG. 30 rotational ring as chain linked form (can also be
inverted without ring but in ring formation--for example as well as
numerous links).
[0040] FIG. 31 rotational ring shown with screen--multiple in
longitudinal and latitudinal lines/form (can also be without ring
but in ring formation--for example).
[0041] FIG. 32 rotational ring shown with screen--multiple in
latitudinal lines/form (can also be without ring but in ring
formation--for example).
[0042] FIG. 33 rotational ring shown with screen-pierced
form--multiple piercing (can also be without ring but in ring
formation--for example--solid metal/material with pierced formation
can also be in other forms as well as geometric--for example).
[0043] FIG. 34 rotational ring shown with screen--multiple in
longitudinal lines/form (can also be without ring but in ring
formation--for example).
[0044] FIG. 35 rotational ring shown with screen--multiple in
longitudinal and latitudinal lines/form (thicker/bolder form, can
also be without ring but in ring formation--for example).
[0045] FIG. 36 rotational ring shown with screen--multiple in
longitudinal and latitudinal lines/form--pierced (can also be
without ring, and can be in other forms as well as geometric--for
example).
[0046] FIG. 37 rotational ring shown with screen and multiple vanes
(variance raised/lowered in degrees)--screen in longitudinal and
latitudinal lines/form. Multiple vanes with screen (multiples of 2
and or odd numbers). Apparatus can also be without ring but in ring
formation--for example.
[0047] FIG. 38 rotational ring shown with screen and multiple vanes
(variance raised/lowered in degrees)--screen in latitudinal
lines/form. Multiple vanes with screen (multiples of 2 and/or odd
numbers). Apparatus can also be without ring but in ring
formation--for example.
[0048] FIG. 39 rotational ring shown with screen-pierced form and
multiple vanes (variance raised/lowered in degrees)--multiple
piercing. Multiple vanes with screen (multiples of 2 and/or odd
numbers). Apparatus can also be without ring but in ring formation
(solid metal/material with pierced formation, can also be in other
forms as well as geometric--for example). FIGS. 46a-46d shown as
internal mesh for the pierced mechanism; this can also be used for
numerous functions in accordance to the mechanism.
[0049] FIG. 40 rotational ring shown with screen and multiple vanes
(variance raised/lowered in degrees) screen longitudinal
lines/form. Multiple vanes with screen (multiples of 2 and/or odd
numbers). Apparatus can also be without ring but in ring
formation--for example.
[0050] FIG. 41 rotational ring shown with screen and multiple vanes
(variance raised/lowered in degrees)--screen in longitudinal and
latitudinal lines/form (thicker/bolder form). Multiple vanes with
screen (multiples of 2 and/or odd numbers). Apparatus can also be
without ring but in ring formation--for example.
[0051] FIG. 42 rotational ring shown with screen and multiple vanes
(variance raised/lowered in degrees)--screen in longitudinal and
latitudinal lines/form--pierced (can be in other forms as well as
geometric). Multiple vanes with screen (multiples of 2 and/or odd
numbers). Apparatus can also be without ring but in ring
formation--for example.
[0052] FIG. 43 rotational ring shown with screen--screen consists
of multiple vanes (variance raised/lowered in degrees), with or
without treads/threads--for example.
[0053] FIG. 44 rotational ring shown with screen--screen in
longitudinal and latitudinal lines/form pierced (can be in other
forms as well as geometric).
[0054] FIG. 45 rotational ring shown in cube form with height,
width, and depth--multiple cubes (can also be without ring but in
ring formation--for example--solid metal/material with or without
cubes consisting a mesh, in multiples of 2 and/or odd numbers.
Note: cube can take other geometric forms.
[0055] FIGS. 46a, 46b, 46c, and 46d consists in variance in
meshing: [0056] (a) is latitudinal, variance in degrees of
aperture. [0057] (b) is latitudinal and longitudinal and variance
in the degrees of aperture (dense.) [0058] (c) is longitudinal,
variance in degrees of aperture. [0059] (d) is latitudinal and
longitudinal variance in degrees of aperture.
[0060] FIG. 47 the guard/cap shown as conical/cone, with multiple
longitudinal and latitudinal lines/vanes form (rectangular-convex
nose of the guard.
[0061] FIG. 48 the guard/cap shown as conical/cone, with multiple
longitudinal and latitudinal lines/vanes form (convex nose of the
guard with smaller scale of graduating metal/material or larger
scale of metal/material).
[0062] FIG. 49 the guard/cap shown as conical/cone, with solid form
(convex nose guard).
[0063] FIG. 50 the guard/cap shown as conical/cone, with multiple
slits in longitudinal lines/vanes form (convex nose guard).
[0064] FIG. 51 the guard/cap shown as conical/cone, with multiple
longitudinal lines/vanes form (convex nose guard).
[0065] FIG. 52 the guard/cap shown as conical/cone, pierced
form--multiple in piercing (convex nose guard can also be in other
forms as well as geometric).
[0066] FIG. 53 the guard/cap shown as conical/cone with multiple
latitudinal line/vanes form (convex nose and/or guard with nose
guard with cylindrical latitude form). FIG. 53 can also be formed
with latitudinal line/vanes without being cylindrical.
[0067] FIG. 54 the guard/cap shown as conical/cone, pierced
form--multiple in piercing as well as longitudinal lines/vanes form
(convex nose can also be in other forms--latitudinal lines may also
be added for additional obstruction.
[0068] FIG. 55 the guard/cap shown as conical/cone, with multiple
longitudinal lines/vanes for greater gas separation with external
centrifuge manifold particle collector-separator.
[0069] FIG. 56 the conical with multiple external vanes (vane
variance raised and/or lowered in degrees)--solid and/or partial
form (for example).
[0070] FIG. 57 the rhombus structural support frame with or without
internal rotational systems, with or without treads/threads--for
example, the rotational system is shown in rectangular form this is
one of many configurations of the structural support frame.
[0071] FIG. 58 the parallelogram structural support frame with or
without internal rotational systems, with or without
treads/threads--for example, the rotational system is shown in
rectangular form this is one of many configurations of the
structural support frame.
[0072] FIG. 59 the spherical/round structural support frame with or
without internal rotational systems, with or without
treads/threads--for example, the rotational system is shown in
rectangular form this is one of many configurations of the
structural support frame.
[0073] FIG. 60 nose guard/cap shown as conical/cone form is solid
formation (cone pointed).
[0074] FIG. 61 nose guard/cap shown as conical/cone form has
multiple longitudinal and latitudinal lines/vanes form (cone
pointed).
[0075] FIG. 62 nose guard/cap shown as conical/cone form is solid
formation (convex form).
[0076] FIG. 63 nose guard/cap shown as conical/cone form has
multiple longitudinal and latitudinal lines/vanes form (convex
form).
[0077] FIG. 64 nose guard/cap shown as conical/cone form is solid
formation (rectangular form).
[0078] FIG. 65 nose guard/cap shown as conical/cone form has
longitudinal and latitudinal lines/vanes form (rectangular
form).
[0079] FIG. 66 nose guard/cap shown as conical/cone form is solid
formation (concave form).
[0080] FIG. 67 nose guard/cap shown as conical/cone form has
longitudinal and latitudinal lines/vanes form (concave form).
DETAILED DESCRIPTION
[0081] FIG. 1 is the first embodiment exhibited in a isometric
partial view of apparatus and noted that the guards/caps and/or
screens (can be interchanged) is shown with longitudinal and
latitudinal form. This embodiment as well as the other embodiment
may consist of a dispersing effect and/or retraction. In FIG. 1
numeral 10a and 10b we note the screens, can be fixed/secured
adhered, positioned and/or attached to the bases of the apparatus
(can be separate apparatus), and thus fastened. The centrifuge
chamber/manifold particle collector exhibited by numerals 12a and
12b. The particle separator exhibits a pair of spaced walls--the
screens--for example--(pierced screen shown as FIG. 33--can be
internal part of the meshed screen(s) with vane(s)--for
example--shown as FIGS. 46a thru 46d) with rotational systems
apparatus--exhibited by numerals 14a and 14b as well as numerals
14c and 14d, with or without treads/threads--for example. Define as
annular passageway there between, having at opposite ends thereof
and outlet flow of communication through two ducts exhibited by
numerals 16a and 16b located at opposite ends of the chamber. The
vanes in the chamber exhibited by numeral 12a and 12b axially
divide the chamber and define an annular extraction manifold. The
three turning vanes each of which extends an arcuate distance of
approximately 120 degrees, (for example) it can be seen that no
particle need travel more than a circumferential distance of 120
degrees (for example) before entering the extraction manifold from
which rebound into the engine inlet is reduced. Variances in
degrees can occur with structural configuration of guard(s)/cap(s)
and/or screens(s). Number of collector vanes may vary to meet the
required amount for collector/separator efficiency. The ducts are
in direct communication with the collection chambers exhibited by
numerals 18a and 18b, and thus the collection chamber is in direct
communication with the two conduits exhibited by numerals 20a and
20b. The chamber 18a, 18b may including mesh for aerodynamic
purposes in various forms as discussed herein.
[0082] As air numeral 22, passes through the inlet which is at a
high velocity it is turned or centrifuged circumferentially at such
a downstream of the vanes, the air has both angular and axial
velocity. This is known as imparting "swirl" to the fluid stream.
Small particles of foreign matter entrained in the air stream are
also centrifuged, having small mass the particles are carried along
with the swirling air. The particles with greater mass are not of
our concern due to the guard(s)/cap(s) and/or screen(s) are used
for preventive measure. A particle entrained in the air stream and
centrifuged will have both tangential and axial velocity downstream
of the turning vanes. Both tangential and axial velocity in theory
not subjected to external forces travel in a straight line path to
the outer periphery of the passage way. In practice, the swirling
air has significant effect on the particles trajectory which can be
compared roughly to that of a helix having increasing diameter in
the downstream direction (as known). Thus the centrifuging and the
entrainment through the turning vanes numeral 12a and 12b and into
the extraction manifold from which particles are collected through
the ducts numerals 16a and 16b. The rotational systems on the
chamber exhibited as numerals 14c and 14d shall additionally enable
the centrifuge process to be enacted (with or without
treads/threads--for example); as well as the engine shaft attached
apparatus being major components.
[0083] The gaseous fluid or air shown as numeral 22 entering the
engine through the inlet passes through the compressor numeral 24
where it is compressed, and hence to the combustor numeral 26 where
the air is mixed with fuel and burned. The hot gases of combustion
emerges at high velocity from the combustor numeral 26 and passes
sequentially through the high pressure turbine numeral 28 and low
pressure turbine numeral 30 where gases are expanded to extract
energy there from. Energy extracted from the hot gases by turbine
numeral 28 provides the driving force for the compressor numeral 24
which is connected to turbine 28 by shaft numeral 32a. Energy
extracted from the hot gases by turbine numeral 30 provides the
driving force for the main engine drive shaft numeral 32b which
delivers power to an energy using device, such as helicopter rotor
system, (not exhibited). After exiting turbine numeral 30 the hot
gases of combustion passes through the engine exhaust duct numeral
34 which includes diffuser numeral 36 in which case gases are
expanded and exit the engine numeral 38. This is the formal
function of numerous jet engines.
[0084] Ejector systems FIG. 6 numeral 40 includes control valve
FIG. 6 numeral 42 for controlling the amount of air bled from the
compressor numeral 24 thus flow of the fluid through the conduits
numerals 20a and 20b to increase efficiency of the gas turbine
engine. When particle collector separation is not deemed necessary
the ejector system may be used to interrupt the flow of bled air. A
modulating valve FIG. 6 numeral 44 regulates the flow in the
conduit thereby increasing engine efficiency. The guards/caps
and/or screens as well as the rotational system shown in FIG. 1
numeral 10a and 10b as well as in FIG. 31 thru FIG. 56 (of
metal/material) can be fastened inside the air inlet of the
aircraft; as well as fastened to the nacelle exterior portion;
and/or in the air inlet extending out to the nacelle. This is also
held true for FIG. 59 the spherical and/or round structural support
frame, with or without rotational system and/or treads/threads
shown as serrated (for example). The support frame can take
numerous forms such as illustrated in FIG. 57 (rhombus) and FIG. 58
(parallelogram), for example. The guards/caps and/or screens can be
fixed to the guards and/or guard frame and/or as separate
apparatus. Numeral 14a and 14b exhibits the rotational systems
noted in rectangular form--this is one of the manipulations shown
in FIG. 25. The rotational systems can be fixed to the guards cowls
and/or base or as a separate apparatus (of metal/material); thus
the rotational systems 14a, 14b, 14c, and 14d can be fixed/
secured, adhered and/or attached to the nacelle/air inlet.
[0085] FIG. 1 numeral 46a and 46b (16 extensions/rods in each
guards/caps and/or screen--for example)--can be separate
apparatus--exhibits extension(s)/rod(s) which can be fixed/secured,
adhered, and/or attached to the guard/cap and/or screens; as well
as, can be fixed/secured, adhered and/or attached to the engine
shaft apparatus and/or pole. These extensions/rods numeral 46a and
46b can extend from the inward and/or outward portion of the
guards/caps and/or screens; or from the screens latitudinal vane(s)
and fixed in the inward portion of the screen as exhibited
(extensions/rods 46a and 46b can also be in multiples of 2/numerous
in numbers and/or odd numbers--of metal/material), are
fixed/secured, positioned and/or adhered to numeral 48a and 48b,
which exhibits the treads/threads of the rotational systems
allowing function to occur. Extensions/Rods can also take a lacing
configuration and/or a longitudinal configuration as well as having
a curved aperture (for example). Thus the treads/threads (for
example) of the rotational systems production of various functions
and movement allows gas separation to occur--examples of movement
and function is swift, pivot, clockwise (for example), time
delayed, auto-mated systems and/or hydraulics (for example--and/or
for opening or closure of apparatus). Numeral 32b exhibits the
engine shaft extension(s) attachment and/or pole (of
metal/material) thus adhered, fixed/secured and/or attached to the
guards/caps, screens and/or extensions. Numeral 32a exhibits shaft
from the high pressure turbine. Numeral 50a, 50b and 50c the
secure/fixed, adhered, apparatus (of metal/material) attached to
the engine and to the engine shaft extension(s) and/or pole-screens
that allows apparatus to be secure/fixed. Therefore, also allowing
the continuous motion from the engine to occur without obstruction
or further automation thereby inducing motion and creating the
rotation and/or function for gas separation to occur without
minimizing engine thrust a higher performance engine has been
created. Since the particles of matter are of small nature due to
the guard(s)/cap(s) and/or screen(s) in not allowing large matter
to be ingested, particles may also remain in the collection
chamber(s) which can be enclosed once particles enter from the
duct(s), thereby offering an additional solution to this problem.
The collection chamber 18a, 18b may include a mesh as discussed
above. This is a prime solution not only for numerous engines--jet,
turboprop, turboshaft as well as for helicopters and other
VTOL/VSTOL aircraft. This is a prime solution for engines and power
plants and the like. Thus a guard(s)/cap(s) and/or screens along
with the mechanism is significant. A casing may be added as deemed
fit shown as numeral 52.
[0086] The following apparatus are various manipulations of the
rotational systems (FIG. 23 thru FIG. 45--rotational systems and/or
screens/guards are of metal/material and can be in numerous
forms--thus for example) can be separate apparatus and/or
secured/fixed, adhered and/or attached to the cowls and/or base
with or without treads/threads--as well as numerous methods can be
used other than treads/threads (for example). Variance in raised
and or lowered in degrees of vanes, may also take a fly wheel
composition FIG. 37 thru FIG. 43 allowing additional gas separation
to occur and turbine motion as well as used in guards (can be used
with conicals/cones). The addition of a mesh FIGS. 46a thru 46d can
be used in FIG. 23 thru FIG. 45 and in other mechanisms. Devices
may also be stationary for other engines and power plants and the
like. All devices are independent (and may also have a curved
aperture--for example) and thus can be interchanged on all
apparatuses.
[0087] FIG. 23 illustrates a rotational ring with serrated form
(can also be inverted) shown to adhere to the cowls and/or base,
with or without treads/threads.
[0088] FIG. 24 rotational ring with jagged form (can also be
inverted) shown to adhere to the cowls and/or base, with and
without treads/threads.
[0089] FIG. 25 rotational ring with rectangular form (can also be
inverted) shown to adhere to the cowls and/or base, with or without
treads/threads.
[0090] FIG. 26 rotational ring with jagged interlocked form (can
also be inverted) shown to adhere to the cowls and/or base, with or
without treads/threads.
[0091] FIG. 27 rotational ring with interlocked form (can also be
inverted) shown to adhere to the cowls and/or base, with or without
treads/threads.
[0092] FIG. 28 rotational ring as coiled form (can also be inverted
without ring but in ring formation--for example--as well as
numerous coils) shown to adhere to the cowls and/or base, with or
without treads/threads.
[0093] FIG. 29 rotational ring as slotted form (can also be
inverted on the outside as well as internal portion of the
ring--for example as well as numerous slots) shown to adhere to the
cowls and/or base, with or without treads/threads.
[0094] FIG. 30 rotational ring as chain linked form (can also be
inverted without ring but in ring formation--for example as well as
numerous links) shown to adhere to the cowls and/or base, with or
without treads/threads.
[0095] FIG. 31 rotational ring shown with screen--multiple in
longitudinal and latitudinal lines/form (can also be without ring
but in ring formation--for example) shown to adhere to the cowls
and/or base, with or without treads/threads.
[0096] FIG. 32 rotational ring shown with screen--multiple in
latitudinal lines/form (can also be without ring but in ring
formation--for example) shown to adhere to the cowls and/or base,
with or without treads/threads.
[0097] FIG. 33 rotational ring shown with screen-pierced
form--multiple piercing (can also be without ring--for
example--solid metal/material with pierced cube formation, can also
be in other forms as well as geometric) shown to adhere to the
cowls and/or base, with or without treads/threads.
[0098] FIG. 34 rotational ring shown with screen--multiple in
longitudinal lines/form (can also be without ring but in ring
formation--for example) shown to adhere to the cowls and/or base,
with or without treads/threads.
[0099] FIG. 35 rotational ring shown with screen--multiple in
longitudinal and latitudinal lines/form (thicker/bolder form, can
also be without ring but in ring formation--for example) shown to
adhere to the cowls and/or base, with or without
treads/threads.
[0100] FIG. 36 rotational ring shown with screen--multiple in
longitudinal and latitudinal lines/form--pierced triangles (can
also be without ring--for example and can be in other forms as well
as geometric) shown to adhere to the cowls and/or base, with or
without treads/threads.
[0101] FIG. 37 rotational ring shown with screen and multiple
vanes--screen in longitudinal and latitudinal lines/form. Multiple
vanes with screen (multiples of 2 and/or odd numbers). Apparatus
can also be without ring but in ring formation (for example).
[0102] FIG. 38 rotational ring shown with screen and multiple
vanes--screen with multiple vanes--screen in latitudinal
lines/form. Multiple vanes with screen (multiple of 2 and/or odd
numbers). Apparatus can also be without ring but in ring formation
(for example).
[0103] FIG. 39 rotational ring shown with screen-pierced form and
multiple vanes--multiple cube piercing. Multiple vanes with screen
(multiples of 2 and/or odd numbers). Apparatus can also be without
ring but in ring formation--for example (solid metal/material with
pierced formation, can also be in other forms as well as
geometric)--for example. FIGS. 46a thru 46d shown as the internal
mesh for pierced mechanism; this mesh can also be used in other
mechanisms and/or manipulations.
[0104] FIG. 40 rotational ring shown with screen and multiple
vanes--screen in longitudinal lines/form. Multiple vanes with
screen (multiples of 2 and/or odd numbers). Apparatus can also be
without ring but in ring formation (for example).
[0105] FIG. 41 rotational ring shown with screen and multiple
vanes--screen in longitudinal and latitudinal lines/form
(thicker/bolder form). Multiple vanes with screen (multiples of 2
and/or odd numbers). Apparatus can also be without ring but in ring
formation (for example).
[0106] FIG. 42 rotational ring shown with screen and multiple
vanes--screen in longitudinal and latitudinal lines/form--pierced
triangular form (can be in other forms as well as geometric).
Multiple vanes with screen (multiples of 2 and/or odd numbers).
Apparatus can also be without ring but in ring formation (for
example).
[0107] FIG. 43 rotational ring shown with screen and multiple
vanes. Multiples of vanes 2 and/or odd numbers. Apparatus can also
be without ring but in ring formation (for example).
[0108] FIG. 44 rotational shown with screen--screen in longitudinal
and latitudinal lines/form pierced triangular form (can be in other
forms as well as geometric compositions).
[0109] FIG. 45 rotational ring shown in cube form with height,
width, and depth--multiple cubes (can also be without ring but in
ring formation--for example--solid metal/material that may have
cubes consisting of a internal, side and/or bottom mesh in
multiples of 2 and/or odd numbers--for example. Note: cube can take
other geometric forms.
[0110] FIGS. 46a, 46b, 46c and 46d consists in variance in meshing:
[0111] (a) is latitudinal, variance in degree of aperture. [0112]
(b) is latitudinal and longitudinal and variance in degrees of
aperture (dense). [0113] (c) is longitudinal variance in degree of
aperture. [0114] (d) is latitudinal and longitudinal variance in
degrees of aperture.
[0115] The following apparatus are various manipulations of the
guards/caps with conical/cones (apparatus can be independent),
shown with cowls and/or base can be fixed/secured, adhered and/or
attached; thus by being fixed/secured, adhered, and/or attached to
the rotational rings (apparatus can be separate) of FIG. 1 numerals
14a and 14b with or without treads/threads. Extensions/Rods FIG. 1
numerals 46a and 46b (apparatus can be independent and may have a
curved aperture), can be fixed/secured, adhered, positioned and/or
attached to the guards/caps and/or screens; as well as to the
engine shaft extension attachment and/or pole, and/or rotational
systems apparatus. All guard/cap noses can be convex/concave,
pointed and solid (for example) as well as other manipulations
listed (apparatus independently and/or whole can be of
metal/material);
[0116] FIG. 47 the guard/cap shown as conical/cone, with multiple
longitudinal and latitudinal lines/vanes form (rectangular--convex
nose of the guard) shown to adhere to the cowls and/or base, as
well as adhering to the rotational rings numerals 14a and 14b with
or without treads/threads; thus can be applied to FIG. 23 thru
FIGS. 45, 57, 58 and 59 respectively.
[0117] FIG. 48 the guard/cap shown as conical/cone, with multiple
longitudinal and latitudinal lines/vanes form (convex nose of the
guard with smaller scale of graduating metal/material or larger
scale of metal/material--the nose of the guard/cap can be
interchanged with other manipulations) shown to adhere to the cowls
and/or base, as well as adhering to the rotational rings numerals
14a and 14b with or without treads/threads; thus can be applied to
FIG. 23 thru FIGS. 45, 57, 58 and 59 respectively.
[0118] FIG. 49 the guard/cap shown as conical/cone, solid form
(convex nose guard) shown to adhere to the cowls and/or base, as
well as adhering to the rotational rings numeral 14a and 14b with
or without treads/threads; thus can be applied to FIG. 23 thru
FIGS. 45, 57, 58, and 59 respectively.
[0119] FIG. 50 the guard/cap shown as conical/cone, with multiple
longitudinal lines/vanes form (convex nose guard) shown to adhere
to the cowls and/or base, as well as adhering to the rotational
rings numeral 14a and 14b with or without treads/threads; thus can
be applied to FIG. 23 thru FIGS. 45, 57, 58 and 59 respectively.
Not shown, although deemed fit is the conical/cone, with multiple
latitudinal lines/vanes form (convex nose guard) thus can adhere to
the cowls and/or base, as well as adhering to the rotational rings
numeral 14a and 14b with or without treads/threads; thus can be
applied to FIG. 23 thru FIGS. 45, 57, 58 and 59 respectively.
[0120] FIG. 51 the guard/cap shown as conical/cone, with multiple
longitudinal lines/vanes form (convex nose guard) shown to adhere
to the cowls and/or base, as well as adhering to the rotational
rings numerals 14a and 14b with or without treads/threads; thus can
be applied to FIG. 23 thru FIGS. 45, 57, 58 and 59
respectively.
[0121] FIG. 52 the guard/cap shown as conical/cone, pierced
triangular form--multiple in piercing (convex nose guard, can be
various patterns of piercing) shown to adhere to the cowls and/or
base, as well as adhering to the rotational rings numerals 14a and
14b with or without treads/threads; thus can be applied to FIG. 23
thru FIGS. 45, 57, 58 and 59 respectively.
[0122] FIG. 53 the guard/cap shown as conical/cone, with multiple
latitudinal lines/vanes form (convex nose guard with nose guard
and/or with cylindrical latitude form as conical/cone) shown to
adhere to the cowls and/or base, as well as adhering to the
rotational rings numerals 14a and 14b with or without
treads/threads; thus can be applied to FIG. 23 thru FIGS. 45, 57,
58 and 59 respectively. Note, conical/cone may also take a
latitudinal line/vanes.
[0123] FIG. 54 the guard/cap shown as conical/cone pierced
triangular form--multiple piercing as well as longitudinal form
(convex nose can also be in other forms--with the addition of
latitudinal lines/vanes may offer additional obstruction shown to
adhere to the cowls and/or base, as well as adhering to the
rotational rings numerals 14a and 14b with or without
treads/threads; thus can be applied to FIG. 23 thru FIGS. 45, 57 58
and 59 respectively.
[0124] FIG. 55 the guard/cap shown as conical/cone with multiple
longitudinal lines/vanes (convex nose guard) and centrifuge process
on the exterior of the conical/cone thus offering centrifuging
process by turning vanes each extending an arcuate distance of
approximately 120 degrees, (for example), shown to adhere to the
cowls and/or base, as well as adhering to the rotational ring
numerals 14a and 14b with or without treads/threads; thus can be
applied to FIG. 23 thru FIGS. 45, 57, 58 and 59 respectively. Note:
conical/cone may also take a latitudinal lines/vanes--not
shown.
[0125] FIG. 56 the guard/cap shown as conical/cone with multiple
longitudinal lines/vanes (convex nose guard) with exterior of a
series of turning vanes each extending an arcuate distance of
approximately 120 degrees--for example (degrees may vary depending
on how may vanes are added to the conical/cone); shown to adhere to
the cowls and/or base, as well as adhering to the rotational ring
numerals 14a and 14b with or without treads/threads; thus can be
applied to FIG. 23 thru FIGS. 45, 57, 58 and 59 respectively. This
conical is prime for deflecting shrapnel and thus returning
shrapnel to the enemy without causing obstruction to engine
components and yet offer maximization of gas separation. Note;
conical/cone may also take a latitudinal lines/vanes--not
shown.
[0126] The following device is the "Structural Support Frame
System," if for numerous jets, turboprop, turboshaft, and other
VTOL/VSTOL as well as engines and power plants and the like; with
or without rotational system as well as with or without
treads/threads (for example). Rotational system may be within the
structural support frame and/or prior to the structural support
fame and/or henceforth after. Possible inclusion, of the
guard(s)/cap(s) and/or screen(s) with the "Structural Support Frame
System."
[0127] FIG. 57 the structural support frame system shown in rhombus
form with rectangular rotational system shown as FIG. 25, can be
fixed/secured, adhered, and/or attached inside the air inlet of the
aircraft, as well as fastened to the nacelle exterior portion,
and/or in the air inlet extending out the nacelle (of
metal/material).
[0128] FIG. 58 the structural support frame system shown in
parallelogram form with rectangular rotational system shown as FIG.
25 can be fixed/secured, adhered, and/or attached inside the air
inlet of the aircraft as well as fastened to the nacelle exterior
portion, and/or in the air inlet extending out the nacelle (of
metal/material).
[0129] FIG. 59 the structural support frame system shown in
spherical and/or round form with rectangular rotational system
shown as FIG. 25 can be fixed/secured, adhered, and/or attached
inside the air inlet of the aircraft as well as fastened to the
nacelle exterior portion, and/or in the air inlet extending out to
the nacelle (of metal/material).
[0130] The following apparatus are nose guards/caps shown in
conical/cone form with various interchanging nose guard/cap--may
take the configuration of convex, concave and/or solid--for
example. All nose guards are independent and thus can be applicable
and interchangeable on all conicals/cones. The following are
manipulations of the conical/cones nose guards/caps:
[0131] FIG. 60 nose guard/cap shown as conical/cone form is solid
formation (cone pointed). Such nose guard/cap can be solid in whole
and/or partial and in kind.
[0132] FIG. 61 nose guard/cap shown as conical/cone form has
multiple longitudinal and latitudinal lines/vanes form (cone
pointed). Such a nose guard/cap can be solid in whole and/or
partial and in kind.
[0133] FIG. 62 nose guard/cap shown as conical/cone form is solid
formation (convex form). Such a nose guard/cap shown can be solid
in whole and/or partial and in kind.
[0134] FIG. 63 nose guard/cap shown as conical/cone form has
multiple longitudinal and latitudinal lines/vanes form (convex
form). Such a nose guard/cap shown can be solid in whole and/or
partial and in kind.
[0135] FIG. 64 nose guard/cap shown as conical/cone form is solid
formation (rectangular form). Such a nose guard/cap shown can be
solid in whole and/or partial and in kind.
[0136] FIG. 65 nose guard/cap shown as conical/cone form has
longitudinal and latitudinal lines/vanes form (rectangular form).
Such a nose guard/cap shown can be solid in whole and/or partial
and in kind.
[0137] FIG. 66 nose guard/cap shown as conical/cone form is solid
formation (concave form). Such a nose guard/cap shown can be solid
in whole and/or partial and in kind.
[0138] FIG. 67 nose guard/cap shown conical/one form has
longitudinal and latitudinal lines/vanes form (concave form). Such
a nose guard/cap can be solid in whole and/or partial and in
kind.
[0139] FIG. 2 illustrates an alternate embodiment exhibited in a
isometric partial view of apparatus and illustrates that the
guards/caps and/or screens (can be interchanged) is shown with
longitudinal and latitudinal form. In FIG. 2 numeral 10a the
screens, can be fixed/secured, adhered, positioned and/or attached
to the bases of the apparatus (can be separate apparatus), and thus
fastened. The centrifuge chamber/manifold particle collector
exhibited by numerals 12a and 12b. The particle separator exhibits
a pair of spaced walls--within the conical/cone--for
example--(pierced screen shown as FIG. 33--can be internal part of
the meshed screen(s) with vane(s)--for example--shown as FIGS. 46a
thru 46d) with rotational systems apparatus--exhibited by numerals
14a with or without treads/threads--for example. Define as annular
passageway there between, having at opposite ends thereof and
outlet flow of communication through two ducts exhibited by
numerals 16a and 16b located at opposite ends of the chamber. The
vanes in the chamber exhibited by numeral 12a and 12b axially
divide the chamber and define an annular extraction manifold within
the conical/cone. The three turning vanes each of which extends an
arcuate distance of approximately 120 degrees, (for example) it can
be seen that no particle need travel more than a circumferential
distance of 120 degrees (for example) before entering the
extraction manifold from which rebound into the engine inlet is
reduced. Variances in degrees can occur with structural
configuration of guard(s)/cap(s) and/or screens(s). Number of
collector vanes may vary to meet the required amount for
collector/separator efficiency. The ducts are in direct
communication with the collection chambers exhibited by numerals
18a and 18b, and thus the collection chamber is in direct
communication with the two conduits exhibited by numerals 20a and
20b. As air numeral 22, passes through the inlet which is at a high
velocity it is turned or centrifuged circumferentially at such a
downstream of the vanes, the air has both angular and axial
velocity. This is known as imparting "swirl" to the fluid stream.
Small particles of foreign matter entrained in the air stream are
also centrifuged, having small mass the particles are carried along
with the swirling air. The particles with greater mass are not of
our concern due to the guard(s)/cap(s) and/or screen(s) are used
for preventive measure. A particle entrained in the air stream and
centrifuged will have both tangential and axial velocity downstream
of the turning vanes. Both tangential and axial velocity in theory
not subjected to external forces travel in a straight line path to
the outer periphery of the passage way. In practice, the swirling
air has significant effect on the particles trajectory which can be
compared roughly to that of a helix having increasing diameter in
the downstream direction (as known). Thus the centrifuging and the
entrainment through the turning vanes numeral 12a and 12b into the
extraction manifold from which particles are collected through the
ducts numerals 16a and 16b. The engine shaft attached apparatus
numeral 32b is thus being major a component in allowing auto
induced function for the rotational and centrifuge process to occur
within the conical/cone. The gaseous fluid or air shown as numeral
22 entering the engine through the inlet passes through the
compressor numeral 24 where it is compressed, and hence to the
combustor numeral 26 where the air is mixed with fuel and burned.
The hot gases of combustion emerges at high velocity from the
combustor numeral 26 and passes sequentially through the high
pressure turbine numeral 28 and low pressure turbine numeral 30
where gases are expanded to extract energy there from. Energy
extracted from the hot gases by turbine numeral 28 provides the
driving force for the compressor numeral 24 which is connected to
turbine 28 by shaft numeral 32a. Energy extracted from the hot
gases by turbine numeral 30 provides the driving force for the main
engine drive shaft numeral 32b which delivers power to an energy
using device, such as helicopter rotor system, (not exhibited).
After exiting turbine numeral 30 the hot gases of combustion passes
through the engine exhaust duct numeral 34 which includes diffuser
numeral 36 in which case gases are expanded and exit the engine
numeral 38. This is the formal function of numerous jet engines.
Ejector systems FIG. 6 numeral 40 includes control valve FIG. 6
numeral 42 for controlling the amount of air bled from the
compressor numeral 24 thus flow of the fluid through the conduits
numerals 20a and 20b to increase efficiency of the gas turbine
engine. When particle collector separation is not deemed necessary
the ejector system may be used to interrupt the flow of bled air. A
modulating valve FIG. 6 numeral 44 regulates the flow in the
conduit thereby increasing engine efficiency. The guards/caps
and/or screens as well as the rotational system shown in FIG. 2
numeral 10a as well as in FIG. 31 thru FIG. 56 (of metal/material)
can be fastened inside the air inlet of the aircraft; as well as
fastened to the nacelle exterior portion; and/or in the air inlet
extending out to the nacelle. This is also held true for FIG. 59
the spherical and/or round structural support frame, with or
without rotational system and/or treads/threads shown as serrated
(for example). The support frame can take s numerous forms such as
FIG. 57 rhombus and FIG. 58 parallelogram (for example). The
guards/caps and/or screens can be fixed to the guards and/or guard
frame and/or as separate apparatus. Numeral 14a exhibits the
rotational systems noted in rectangular form--this is one of the
manipulations shown in FIG. 25. The rotational systems can be fixed
to the guards cowls and/or base or as a separate apparatus (of
metal/material); thus to the rotational systems 14a, can be
fixed/secured, adhered and/or attached to the nacelle/air inlet.
FIG. 2 numeral 46a (16 extensions/rods in the guards/caps and/or
screen--for example)--can be separate apparatus--exhibits
extension(s)/rod(s) which can be fixed/secured, adhered, and/or
attached to the guard/cap and/or screens; as well as, can be
fixed/secured, adhered and/or attached to the engine shaft
apparatus and/or pole apparatus. These extensions/rods numeral 46a
and 46b can extend from the inward and/or outward portion of the
guards/caps and/or screens; or from the screens latitudinal vane(s)
and fixed in the inward portion of the screen as exhibited
(extensions/rods 46a can also be in multiples of 2/numerous in
numbers and/or odd numbers--of metal/material), are fixed/secured,
positioned and/or adhered to numeral 48a, which exhibits the
treads/threads of the rotational systems allowing function to
occur. Extensions/Rods can also take a lacing configuration and/or
a longitudinal configuration as well as a curved aperture (for
example). Thus inventing treads/threads (for example) of the
rotational systems production of various functions and movement
shall therefore allow gas separation to occur--examples of movement
and function is swift, pivot, clockwise (for example), time
delayed, automated systems and/or hydraulics (for example--and/or
for opening or closure of apparatus). Numeral 32b exhibits the
engine shaft extension(s) attachment and/or pole (of
metal/material) thus adhered, fixed/secured and/or attached to the
guards/caps, screens and/or extensions. Numeral 32a exhibits shaft
from the high pressure turbine. Numeral 50a, the secure/fixed,
adhered, apparatus (of metal/material) attached to the engine and
to the engine shaft apparatus and/or pole-screens that allows
apparatus to be secure/fixed. Therefore, also allowing the
continuous motion from the engine to occur without obstruction or
further automation thereby inducing motion and creating the
rotation and/or function for gas separation to occur without
minimizing engine thrust we have created a higher performance
engine. Note: Since the particles of matter are of small nature due
to the guard(s)/cap(s) and/or screen(s) in not allowing large
matter to be ingested, particles may also remain in the collection
chamber(s) which can be enclosed once particles enter from the
duct(s), thereby offering an additional solution to this problem.
This is a prime solution not only for numerous engines--jet,
turboprop, turboshaft as well as for helicopters and other
VTOL/VSTOL aircraft. This is a prime solution for engines and power
plants and the like. Thus a guard(s)/cap(s) and/or screens along
with the mechanism is significant. A casing may be added as deemed
fit shown as numeral 52. Alternate screen/guards as illustrated in
FIGS. 23-45 can also be incorporated into the embodiment
illustrated in FIG. 2.
[0140] FIG. 3 shows an isometric partial expanded view of a multi
vane double guards/caps and/or screens with engine attached
apparatus and/or pole, with rotational systems. Centrifuge
chamber/manifold particle collector-separator shown with expanded
view as well as multiple extensions/rods 46a--18 for example,
(exhibited in the inward position towards the security apparatus),
exhibited in FIG. 2.
[0141] FIG. 4 shows an isometric partial view of a multi vane
double guards/caps and/or screens with engine attached apparatus
and/or pole, with rotational systems. Centrifuge chamber/manifold
particle collector-separator shown with expanded view as well as
multiple extensions/rods 46c--18 for example, (exhibited in the
outwards position of the security apparatus).
[0142] FIG. 5 shows a cross-sectional view of the separator
exhibited in FIG. 1 numerals 12a and 12b, as well as exhibited in
FIG. 2 numerals 12a and 12b. Thus the separator--three turning
vanes each of which extends an arcuate distance of approximately
120 degrees, (for example) it can be seen that no particle need
travel more than a circumferential distance of 120 degrees (for
example) before entering the extraction manifold from which rebound
into the engine inlet is reduced. Variances in degrees can occur
with structural configuration of guard(s)/cap(s) and/or screen(s),
we note that separators turning vanes in FIG. 1 and FIG. 2 are
exhibited on the conical/cone (for example).
[0143] FIG. 6 shows ejector systems numeral 40 includes the control
valve numeral 42 for controlling the amount of air bled from the
compressor FIG. 1 and FIG. 2 numeral 24 thus flow of the fluid
through the conduits FIG. 1 and FIG. 2 numerals 20a and 20b to
increase efficiency of the gas turbine engine. When particle
collector separation is not deemed necessary the ejector system may
be used to interrupt the flow of bled air. A modulating valve
exhibited in FIG. 6 numeral 44 regulates the flow in the conduit
thereby increasing engine efficiency.
[0144] FIG. 7 shows the manifold sectional; thereby attached to the
engine apparatus and/or pole--(apparatus can be single, or
attached, fixed/secured on the engine attached apparatus and/or
pole, or fixed/secured on the guard(s)/cap(s) and/or screen(s).
[0145] FIG. 8 illustrates another alternate embodiment of
Single/Multiple Guard(s)/Cap(s) and/or Screen(s) with Engine
Systems Attached Apparatus and/or Pole with Rotational System(s);
exhibited in a isometric partial view of apparatus and noted that
the guards/caps and/or screens (can be interchanged) is shown with
longitudinal and latitudinal form. In FIG. 8 numeral 58 exhibits
conical/cone with convex nose guard (conicals/cones may be suited
for example are FIG. 47 thru FIG. 56 as well FIG. 10 numeral 60 the
darted conical/cone) exhibiting cowl and/or base as numeral 56
thereby attached to the rotational systems noted in rectangular
form exhibited as numerals 14a and 14b--this is one of the
manipulations shown in FIG. 25. The rotational systems can be fixed
to the guards cowl and/or base or as separate apparatus (of
metal/material); thus the rotational systems 14a and 14b can be
fixed/secured, adhered and/or attached to the nacelle/air inlet.
FIG. 8 numerals 46a and 46b (exhibits extensions/rods--46a--10
extensions/rods, 46b 12 extensions/rods for example) can be
separate apparatus--exhibits extension(s)/rod(s) which can be
fixed/secured, adhered, and/or attached to the guard/cap and or
screens; as well as fixed/ secured, adhered and/or attached to the
engine shaft extension(s) and/or pole apparatus. These
extensions/rods numerals 46a and 46b can extend from the inward
and/or outward portion of the guards/caps and/or screens; or from
the screen latitudinal vane(s)--(if screen is added) and
fixed/secured, attached and/or adhered to the inward portion of the
guards/caps and/or screens. Extensions/Rods 46a and 46b can also be
in multiples of 2/numerous in numbers and or odd numbers,
extensions/rods may have a curved aperture for greater gas
separation--of metal/material. Conicals/cones with multi vanes have
a greater degree of gas separation thereby engine to function more
efficiently.
[0146] As air numeral 22, passes through the inlet which is at a
high velocity it is turned at such a downstream by the vanes, the
air has both angular and axial velocity. This is known as imparting
"swirl" to the fluid stream. Small particles of foreign matter
entrained in the air stream are carried along with the swirling
air. The particles with greater mass are not of our concern due to
the guard(s)/cap(s) and/or screen(s) are used for preventive
measure. A particle entrained in the air stream will have both
tangential and axial velocity downstream of the turning vanes. Both
tangential and axial velocity in theory are not subjected to
external forces travel in a straight line path to the outer
periphery of the passage way. In practice, the swirling air has
significant effect on the particles trajectory which can be
compared roughly to that of a helix having increasing diameter in
the downstream direction (as known). The rotational systems
numerals 14a and 14b with or without treads/threads numerals 48a
and 48b shall enable gas separation to take place as well as guard
from foreign objects. The gaseous fluid or air shown as numeral 22
entering the engine through the inlet passes through the compressor
numeral 24 where it is compressed, and hence to the combustor
numeral 26 where the air is mixed with fuel and burned. The hot
gases of combustion emerges at high velocity from the combustor
numeral 26 and passes sequentially through the high pressure
turbine numeral 28 and low pressure turbine numeral 30 where gases
are expanded to extract energy there from. Energy extracted from
the hot gases by turbine numeral 28 provides the driving force for
the compressor numeral 24 which is connected to turbine 28 by shaft
numeral 32a. Energy extracted from the hot gases by turbine numeral
30 provides the driving force for the main engine drive shaft
numeral 32b which delivers power to an energy using device, such as
helicopter rotor system, (not exhibited). After exiting turbine
numeral 30 the hot gases of combustion passes through the engine
exhaust duct numeral 34 which includes diffuser numeral 36 in which
case gases are expanded and exit the engine numeral 38. This is the
formal function of numerous jet engines. Ejector systems as well as
conduits may also be added (not exhibited in FIG. 8 but exhibited
in FIG. 1 and FIG. 2) FIG. 6 numeral 40 includes control valve FIG.
6 numeral 42 for controlling the amount of air bled from the
compressor numeral 24 thus flow of the fluid through the conduits
means numerals 20a and 20b to increase efficiency of the gas
turbine engine. A modulating valve FIG. 6 numeral 44 regulates the
flow in the conduit thereby increasing engine efficiency. The
guards/caps and/or screens as well as the rotational system 14a and
14b shown in FIG. 8 numeral 58 are also deemed appropriate use and
possible to be used in FIG. 31 thru FIG. 56 for example (of metal/
material) thus can be fastened inside the air inlet of the
aircraft; as well as fastened to the nacelle exterior portion;
and/or in the air inlet extending out to the nacelle. This is also
held true for FIG. 59 the spherical and/or round structural support
frame, with or without rotational system and/or treads/threads
shown as serrated (for example). We note support frame can take
numerous forms such as FIG. 57 rhombus and FIG. 58 parallelogram
(for example). The guards/caps and/or screens can be fixed to the
guards and/or guard frame and/or as separate apparatus. Thus
inventing the treads/threads (for example) of the rotational
systems production of various functions and movement shall
therefore allow gas separation to occur--examples of movement and
function is swift, pivot, clockwise (for example), time delayed,
automated systems and/or hydraulics (for example--and/or for
opening or closure of apparatus). Numeral 32b exhibits the engine
shaft extension(s) attachment and/or pole (of metal/material) thus
adhered, fixed/secured and/or attached to the guards/caps, screens
and/or extensions. Numeral 32a exhibits shaft from the high
pressure turbine. Numeral 50a, 50b and 50c the secure/fixed,
adhered, apparatus (of metal/material) attached to the engine and
to the engine shaft extension(s) and/or pole-screens that allows
apparatus to be secure/fixed. Therefore, also allowing the
continues motion from the engine to occur without obstruction or
further automation thereby inducing motion and creating the
rotation and/or function for gas separation to occur without
minimizing engine thrust we have created a higher performance
engine. Note: Since the particles of matter are of small nature due
to the guard(s)/cap(s) and/or screen(s) in not allowing large
matter to be ingested, particles may also remain in the collection
chamber(s) (not exhibited in FIG. 8 but shown in FIG. 1 and FIG. 2
numerals 18a and 18b) but which can be enclosed once particles
enter from the duct(s), thereby offering an additional solution to
this problem. This is a prime solution not only for numerous
engines--jet, turboprop, turboshaft as well as for helicopters and
other VTOL/VSTOL aircraft. This is a prime solution for engines and
power plants and the like. Thus a guard(s)/cap(s) and/or screens
along with the mechanism is significant. A casing may be added as
deemed fit shown in FIG. 1 and FIG. 3 numeral 52.
[0147] FIG. 9 shows an isometric partial expanded view of a double
guards/caps and/or screens with the engine attached apparatus
and/or pole, with rotational system.
[0148] The following apparatus are various manipulations of the
rotational systems (FIG. 23 thru FIG. 45--rotational systems and/or
screens/guards are of metal/material and can be in numerous
forms--thus for example) can be separate apparatus and/or
secured/fixed, adhered and/or attached to the cowls and/or base
with or without treads/threads--as well as numerous methods can be
used other than treads/threads (for example). Variance in raised
and or lowered in degrees of vanes, may also take a fly wheel
composition FIG. 37 thru FIG. 43 allowing additional gas separation
to occur and turbine motion as well as used in guards (can be used
with conicals/cones). The addition of a mesh 46a thru 46d can be
used in FIG. 23 thru FIG. 45 and in other mechanisms. Devices may
also be stationary for other engines and power plants and the like.
All devices are independent (and may also have a curved
aperture--for example) and thus can be interchanged on all
apparatuses. Alternate screen/guards as discussed above and
illustrated in FIGS. 23-45 can also be incorporated into the
embodiment illustrated in FIG. 3.
[0149] FIG. 10 represents another alternate embodiment of
Single/Multiple Guard(s)/Cap(s) and/or Screen(s) with Engine
Systems Retractable Attached Apparatus and/or Pole with Rotational
System(s) exhibited in a isometric partial view of apparatus and
noted that the guards/caps and/or screens (can be interchanged) is
shown with longitudinal and latitudinal form. In FIG. 10 numeral 60
exhibits the darted conical/cone with convex nose guard,
(conicals/cones may be suited for example are FIG. 47 thru FIG. 56)
exhibiting cowl and/or base as numeral 56 and a plurality of spokes
46a, 46b, pivotally attached on one end to the base 56 forming a
cone shape in one position where the spokes 46a, 46b generally
divergent on one end as shown, for example, in FIG. 10 and a one or
more intermediate positions, for example, as shown in FIGS. 12-14
wherein the angle between the spokes 46a, 46b and the shaft 32b is
varied from that shown in FIG. 10. The base 56 may be attached to
the rotational systems noted in rectangular form exhibited as
numerals 14a and 14b--this is one of the manipulations shown in
FIG. 25. The rotational systems can be fixed to the guards cowl
and/or base or as separate apparatus (of metal/material); thus the
rotational systems 14a and 14b can be fixed/secured, adhered and/or
attached to the nacelle/air inlet. FIG. 10 numerals 46a and 46b
(exhibits extensions/rods--46a--10 extensions/rods, 46b 12
extensions/rods for example) can be separate apparatus--exhibits
extension(s)/rod(s) which can be fixed/secured, adhered, and/or
attached to the guard/cap and or screens; as well as fixed/secured,
adhered and/or attached to the engine shaft extension(s) and/or
pole apparatus. These extensions/rods numerals 46a and 46b can
extend from the inward and/or outward portion of the guards/caps
and/or screens; or from the screen latitudinal vane(s), (if screen
is added) and fixed/secured, attached and/or adhered to the inward
portion of the guards/caps and/or screens. Extensions/Rods 46a and
46b can also be in multiples of 2/numerous in numbers and or odd
numbers, extensions/rods may have a curved aperture for greater gas
separation--of metal/material. Conicals/cones with multi vanes have
a greater degree of gas separation thereby engine to function more
efficiently. As air numeral 22, passes through the inlet which is
at a high velocity it is turned at such a downstream by the vanes,
the air has both angular and axial velocity. This is known as
imparting "swirl" to the fluid stream. Small particles of foreign
matter entrained in the air stream are carried along with the
swirling air. The particles with greater mass are not of our
concern due to the guard(s)/cap(s) and/or screen(s) are used for
preventive measure. A particle entrained in the air stream will
have both tangential and axial velocity downstream of the turning
vanes. Both tangential and axial velocity in theory are not
subjected to external forces travel in a straight line path to the
outer periphery of the passage way. In practice, the swirling air
has significant effect on the particles trajectory which can be
compared roughly to that of a helix having increasing diameter in
the downstream direction (as known). The rotational systems
numerals 14a and 14b with or without treads/threads numerals 48a
and 48b shall enable gas separation to take place as well as guard
from foreign objects. The gaseous fluid or air shown as numeral 22
entering the engine through the inlet passes through the compressor
numeral 24 where it is compressed, and hence to the combustor
numeral 26 where the air is mixed with fuel and burned. The hot
gases of combustion emerges at high velocity from the combustor
numeral 26 and passes sequentially through the high pressure
turbine numeral 28 and low pressure turbine numeral 30 where gases
are expanded to extract energy there from. Energy extracted from
the hot gases by turbine numeral 28 provides the driving force for
the compressor numeral 24 which is connected to turbine 28 by shaft
numeral 32a. Energy extracted from the hot gases by turbine numeral
30 provides the driving force for the main engine drive shaft
numeral 32b which delivers power to an energy using device, such as
helicopter rotor system, (not exhibited). After exiting turbine
numeral 30 the hot gases of combustion passes through the engine
exhaust duct numeral 34 which includes diffuser numeral 36 in which
case gases are expanded and exit the engine numeral 38. This is the
formal function of numerous jet engines. Ejector systems and
centrifuge vanes may also be added thus as well as the conduits if
deemed to (not exhibited in FIG. 10 but exhibited in FIG. 1 and
FIG. 2) FIG. 6 numeral 40 includes control valve FIG. 6 numeral 42
for controlling the amount of air bled from the compressor numeral
24 thus flow of the fluid through the conduits means numerals 20a
and 20b to increase efficiency of the gas turbine engine. A
modulating valve FIG. 6 numeral 44 regulates the flow in the
conduit thereby increasing engine efficiency. The guards/caps
and/or screens as well as the rotational system 14a and 14b shown
in FIG. 10 numeral 60 (darted guard) are also deemed appropriate
use and possible to be used in FIG. 31 thru FIG. 56 for example (of
metal/material) thus can be fastened inside the air inlet of the
aircraft; as well as fastened to the nacelle exterior portion;
and/or in the air inlet extending out to the nacelle. This is also
held true for FIG. 59 the spherical and/or round structural support
frame, with or without rotational system and/or treads/threads
shown as serrated (for example). We note support frame can take
numerous forms such as FIG. 57 rhombus and FIG. 58 parallelogram
(for example). The guards/caps and/or screens can be fixed to the
guards and/or guard frame and/or as separate apparatus. Thus
inventing the treads/threads (for example) of the rotational
systems production of various functions and movement shall
therefore allow gas separation to occur--examples of movement and
function is swift, pivot, clockwise (for example), time delayed,
auto-mated systems and/or hydraulics (for example--and/or for
opening or closure of apparatus). Numeral 32b exhibits the engine
shaft extension(s) attachment and/or pole (of metal/material) thus
adhered, fixed/secured and/or attached to the guards/caps, screens
and/or extensions. Numeral 32a exhibits shaft from the high
pressure turbine. Numeral 50a, 50b and 50c the secure/fixed,
adhered, apparatus (of metal/material) attached to the engine and
to the engine shaft extension(s) and/or pole-screens that allows
apparatus to be secure/fixed. Therefore, also allowing the
continuous motion from the engine to occur without obstruction or
further automation thereby inducing motion and creating the
rotation and/or function for gas separation to occur without
minimizing engine thrust we have created a higher performance
engine. Note: Since the particles of matter are of small nature due
to the guard(s)/cap(s) and/or screen(s) in not allowing large
matter to be ingested, particles may also remain in the collection
chamber(s) (not exhibited in FIG. 10 but shown in FIG. 1 numerals
18a and 18b and FIG. 2 numerals 18a and 18b) but which can be
enclosed once particles enter from the duct(s), thereby offering an
additional solution to this problem. Formal retraction process
shall commence by the conical/cone thus with dispersing movement
(shown in FIGS. 12, 13 and 14) by center axis in multiples of 2 in
numbers and/or odd numbers thus retract over the inlet and thus
allow the extensions/rods to commence into a folding and/or are
laced pattern for example as thus the conical/cone may also be
deemed into a folding or laced pattern (shown by isometric partial
expanded view FIG. 11) which shall be taken into account by the
type of inlet of a particular aircraft as well as the type of
engine. This can also be a significant process for other engines
and power plants and the like. FIG. 10 numerals 62a and 62b exhibit
the retraction slots in which case for example the use
hydraulics/automation process shall commence. The retraction
apparatus exhibited as FIG. 10 numerals 64a, 64b, and 64c shall
allow the attached apparatus and/or pole to be condensed within the
pole in a stacking manner or on the exterior portion of the pole in
a stacking matter--for example--FIG. 18 and FIG. 19 exhibit a
expanded view of retractors (this shall very on the type of
aircraft and/or engine). If centrifuge chamber manifold particle
collector is deemed fit to use thus variance on the type of
aircraft and/or engine as well as power plants and the
like--similar process shall commence thereby a folding and/or laced
pattern--for example. Prior works exhibit aircraft--conicals/cones
used for directional purposes by means of hydraulic movement thus
back and forth although a lack of efficiency and energy has not
allowed these types of aircraft to attain the highest performance
deemed possible, by the use of the rotational system(s) and being
cost effective and efficient we attain a higher degree of
performance that allows gas separation to take place as well as
maintaining and not compromising the engine thrust. The multi vane
conical--for example offers a greater degree of gas separation than
a solid conical. Variance in guards/caps and/or screens vanes
and/or mesh offer variances in degrees of gas separation. Thus, the
three centrifuge multi vane conical/cone exhibited as FIG. 55
exhibits offers centrifuge process on the external means of conical
thereby offering as well as direction this is also deemed similar
in nature with FIG. 56 the multi vane centrifuge deflector
conical/cone offers gas separation, directional purposes as well as
deflecting shrapnel from enemies attack. This is a prime solution
not only for numerous engines--jet, turboprop, turboshaft as well
as for helicopters and other VTOL/VSTOL aircraft. This is a prime
solution as well as for engines and power plants and the like. Thus
a guard(s)/cap(s) and/or screens along with the mechanism is
significant. A casing may be added as deemed fit shown in FIG. 1
and FIG. 3 numeral 52.
[0150] FIG. 9 shows an isometric partial expanded view of a double
guards/caps/ and/or screens with the engine attached apparatus
and/or pole, with rotational system. In addition, alternate
screen/guards as discussed above can be incorporated into the
embodiment illustrated in FIG. 10.
[0151] The following apparatus are various manipulations of the
guards/caps with conical/cones (apparatus can be independent),
shown with cowls and/or base can be fixed/secured, adhered and/or
attached; thus by being fixed/secured, adhered, and/or attached to
the rotational rings (apparatus can be separate) of FIG. 1 numerals
14a and 14b with or without treads/threads. Extensions/Rods FIG. 1
numerals 46a and 46b (apparatus can be independent and may have a
curved aperture), can be fixed/secured, adhered, positioned and/or
attached to the guards/caps and/or screens; as well as to the
engine shaft extension attachment and/or pole, and/or rotational
systems apparatus. All guard/cap noses can be convex/concave,
pointed and solid (for example) as well as other manipulations
listed (apparatus independently and/or whole can be of
metal/material):
[0152] FIG. 47 the guard/cap shown as conical/cone, with multiple
longitudinal and latitudinal lines/vanes form (rectangular-convex
nose of the guard) shown to adhere to the cowls and/or base, as
well as adhering to the rotational rings numerals 14a and 14b with
or without treads/threads; thus can be applied to FIG. 23 thru
FIGS. 45, 57, 58 and 59 respectively.
[0153] FIG. 48 the guard/cap shown as conical/cone, with multiple
longitudinal and latitudinal lines/vanes form (convex nose of the
guard with smaller scale of graduating metal/material or larger
scale of metal/material--the nose of the guard/cap can be
interchanged with other manipulations) shown to adhere to the cowls
and/or base, as well as adhering to the rotational rings numerals
14a and 14b with or without treads/threads; thus can be applied to
FIG. 23 thru FIGS. 45, 57, 58 and 59 respectively.
[0154] FIG. 49 the guard/cap shown as conical/cone, solid form
(convex nose guard) shown to adhere to the cowls and/or base, as
well as adhering to the rotational rings numeral 14a and 14b with
or without treads/threads; thus can be applied to FIG. 23 thru
FIGS. 45, 57, 58, and 59 respectively.
[0155] FIG. 50 the guard/cap shown as conical/cone, with multiple
longitudinal lines/vanes form (convex nose guard) shown to adhere
to the cowls and/or base, as well as adhering to the rotational
rings numeral 14a and 14b with or without treads/threads; thus can
be applied to FIG. 23 thru FIGS. 45, 57, 58 and 59 respectively.
Not shown, although deemed fit is the conical/cone, with multiple
latitudinal lines/vanes form (convex nose guard) thus can adhere to
the cowls and/or base, as well as adhering to the rotational rings
numeral 14a and 14b with or without treads/threads; thus can be
applied to FIG. 23 thru FIGS. 45, 57, 58 and 59 respectively.
[0156] FIG. 51 the guard/cap shown as conical/cone, with multiple
longitudinal lines/vanes form (convex nose guard) shown to adhere
to the cowls and/or base, as well as adhering to the rotational
rings numerals 14a and 14b with or without treads/threads; thus can
be applied to FIG. 23 thru FIGS. 45, 57, 58 and 59
respectively.
[0157] FIG. 52 the guard/cap shown as conical/cone, pierced
triangular form--multiple in piercing (convex nose guard, can be
various patterns of piercing) shown to adhere to the cowls and/or
base, as well as adhering to the rotational rings numerals 14a and
14b with or without treads/threads; thus can be applied to FIG. 23
thru FIGS. 45, 57, 58 and 59 respectively.
[0158] FIG. 53 the guard/cap shown as conical/cone, with multiple
latitudinal lines/vanes form (convex nose guard with nose guard
and/or with cylindrical latitude form as conical/cone) shown to
adhere to the cowls and/or base, as well as adhering to the
rotational rings numerals 14a and 14b with or without
treads/threads; thus can be applied to FIG. 23 thru FIGS. 45, 57,
58 and 59 respectively. Note, the conical/cone may also take a
latitudinal lines/vanes.
[0159] FIG. 54 the guard/cap shown as conical/cone pierced
triangular form--multiple piercing as well as longitudinal form
(convex nose can also be in other forms--with the addition of
latitudinal lines/vanes may offer additional obstruction shown to
adhere to the cowls and/or base, as well as adhering to the
rotational rings numerals 14a and 14b with or without
treads/threads; thus can be applied to FIG. 23 thru FIGS. 45, 57 58
and 59 respectively.
[0160] FIG. 55 the guard/cap shown as conical/cone with multiple
longitudinal lines/vanes (convex nose guard) and centrifuge process
on the exterior of the conical/cone thus offering centrifuging
process by turning vanes each extending an arcuate distance of
approximately 120 degrees, (for example), shown to adhere to the
cowls and/or base, as well as adhering to the rotational ring
numerals 14a and 14b with or without treads/threads; thus can be
applied to FIG. 23 thru FIGS. 45, 57, 58 and 59 respectively. Note:
conical/cone may also take a latitudinal lines/vanes--not
shown.
[0161] FIG. 56 the guard/cap shown as conical/cone with multiple
longitudinal lines/vanes (convex nose guard) with exterior of a
series of turning vanes each extending an arcuate distance of
approximately 120 degrees--for example (degrees may vary depending
on how may vanes are added to the conical/cone); shown to adhere to
the cowls and/or base, as well as adhering to the rotational ring
numerals 14a and 14b with or without treads/threads; thus can be
applied to FIG. 23 thru FIGS. 45, 57, 58 and 59 respectively. This
conical is prime for deflecting shrapnel and thus returning
shrapnel to the enemy without causing obstruction to engine
components and yet offer maximization of gas separation. Note;
conical/cone may also take a latitudinal lines/vanes--not
shown.
[0162] The following device is the "Structural Support Frame
System," if for numerous jets, turboprop, turboshaft, and other
VTOL/VSTOL as well as engines and power plants and the like; with
or without rotational system as well as with or without
treads/threads (for example). Rotational system may be within the
structural support frame and/or prior to the structural support
fame and/or henceforth after. Possible inclusion, of the
guard(s)/cap(s) and/or screen(s) with the "Structural Support Frame
System."
[0163] FIG. 57 the structural support frame system shown in rhombus
form with rectangular rotational system shown as FIG. 25, can be
fixed/secured, adhered, and/or attached inside the air inlet of the
aircraft, as well as fastened to the nacelle exterior portion,
and/or in the air inlet extending out the nacelle (of
metal/material).
[0164] FIG. 58 the structural support frame system shown in
parallelogram form with rectangular rotational system shown as FIG.
25 can be fixed/secured, adhered, and/or attached inside the air
inlet of the aircraft as well as fastened to the nacelle exterior
portion, and/or in the air inlet extending out the nacelle (of
metal/material).
[0165] FIG. 59 the structural support frame system shown in
spherical and/or round form with rectangular rotational system
shown as FIG. 25 can be fixed/secured, adhered, and/or attached
inside the air inlet of the aircraft as well as fastened to the
nacelle exterior portion, and/or in the air inlet extending out to
the nacelle (of metal/material).
[0166] The following apparatus are nose guards/caps shown in
conical/cone form with various interchanging nose guard/cap--may
take the configuration of convex, concave and/or solid--for
example. All nose guards are independent and thus can be applicable
and interchangeable on all conicals/cones. The following are
manipulations of the conical/cones nose guards/caps:
[0167] FIG. 60 nose guard/cap shown as conical/cone form is solid
formation (cone pointed). Such nose guard/cap can be solid in whole
and/or partial and in kind.
[0168] FIG. 61 nose guard/cap shown as conical/cone form has
multiple longitudinal and latitudinal lines/vanes form (cone
pointed). Such a nose guard/cap can be solid in whole and/or
partial and in kind.
[0169] FIG. 62 nose guard/cap shown as conical/cone form is solid
formation (convex form). Such a nose guard/cap shown can be solid
in whole and/or partial and in kind.
[0170] FIG. 63 nose guard/cap shown as conical/cone form has
multiple longitudinal and latitudinal lines/vanes form (convex
form). Such a nose guard/cap shown can be solid in whole and/or
partial and in kind.
[0171] FIG. 64 nose guard/cap shown as conical/cone form is solid
formation (rectangular form). Such a nose guard/cap shown can be
solid in whole and/or partial and in kind.
[0172] FIG. 65 nose guard/cap shown as conical/cone form has
longitudinal and latitudinal lines/vanes form (rectangular form).
Such a nose guard/cap shown can be solid in whole and/or partial
and in kind.
[0173] FIG. 66 nose guard/cap shown as conical/cone form is solid
formation (concave form). Such a nose guard/cap shown can be solid
in whole and/or partial and in kind.
[0174] FIG. 67 nose guard/cap shown conical/one form has
longitudinal and latitudinal lines/vanes form (concave form). Such
a nose guard/cap can be solid in whole and/or partial and in
kind.
[0175] FIG. 11 shows an isometric partial expanded view of the
double guards/caps and/or screen with the engine attached apparatus
and/or pole, with rotational systems. The formal process and thus
description of is noted in FIG. 10 although in FIG. 11 we note the
solid partial view conical as numeral 58.
[0176] FIG. 12 shows dispersing of a conical exhibited in numeral
66 and thus exhibiting cowl numeral 56 for retraction process;
conical may take a multiple forms for example FIG. 47 thru FIG. 56.
Dispersing for example may be in multiples of 2 in numbers and/or
odd numbers--of metal/material.
[0177] FIG. 13 shows dispersing of a conical exhibited in numeral
66 and thus exhibiting cowl numeral 56 for retraction process;
conical may take a multiple forms for example FIG. 47 thru FIG. 56.
Dispersing for example may be in multiples of 2 in numbers and/or
odd numbers--of metal/material. Exhibiting also 54a the additional
multi vane conical; as dispersing occurs the multi vane conical is
exhibited to the forefront by hydraulic/automated means to maintain
the integrity of the engine components as dispersing occurs.
[0178] FIG. 14 shows dispersing of a conical exhibited in numeral
66 and thus exhibiting cowl numeral 56 for retraction process;
conical may take a multiple forms for example FIG. 47 thru FIG. 56.
Dispersing for example may be in multiples of 2 in numbers and/or
odd numbers--of metal/material. Exhibiting also 54b the additional
multi vane conical with spherical vanes; as dispersing occurs the
multi vane conical is exhibited to the forefront by
hydraulic/automated means to maintain the integrity of the engine
components as dispersing occurs.
[0179] FIG. 15 shows the engine shaft extension security attachment
and/or pole, diamond form (for example). This device shall allow
security to be maintained without obstruction of function by the
rotational system(s).
[0180] FIG. 16 shows the engine shaft extension security attachment
and/or pole, cylindrical form (for example). This device shall
allow security to be maintained without obstruction of function by
the rotational system(s).
[0181] FIG. 17 shows the engine shaft extension security attachment
and/or pole, in rectangular form (for example). The device shall
allow security to be maintained without obstruction of function by
the rotational system(s).
[0182] FIG. 18 shows the multiple section engine attachment for
retraction process of the apparatus and/or pole, this device may be
used in FIG. 10. Not exhibited although deemed fit is the
multi-laced engine attachment apparatus and/or pole may also have
retracting properties or without (for example).
[0183] FIG. 19 shows multiple section engine attachment for
retraction process of the apparatus and/or pole, exhibited in FIG.
10 numerals 64a, 64b, and 64c.
[0184] FIG. 20 shows longitudinal apparatus and/or pole for
numerous dual inlets, with dual extending apparatus from the pole
for the inlet--thus shall function similar to engine shaft attached
apparatus and/or pole although for a dual inlet. This device may
also be used for other engines and power plants and the like.
[0185] FIG. 21 shows longitudinal engine attached apparatus and/or
pole for inlet, this device may also be used for other engines and
power plants and the like.
[0186] FIG. 22 shows longitudinal attached apparatus and/or pole
for numerous dual inlet, with dual extending apparatus for
both/opposite side of the pole for the inlet, this device may also
be use for other engines and power plants and the like.
[0187] Obviously, many modifications and variations of the present
invention are possible in light of the above teachings. Thus, it is
to be understood that, within the scope of the appended claims, the
invention may be practiced otherwise than as specifically described
above.
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